变攻角下孔隙射流对高负荷扩压叶栅气动性能的影响  

Effect of Air Injection on Aerodynamic Performance of a Highly-loaded Compressor Cascade at Different Incidences

作　　者：冯冬民[1,2] 陈浮[2] 陈焕龙[2] 王仲奇[2] 

机构地区：[1]沈阳发动机设计研究所,辽宁沈阳110015 [2]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《燃气涡轮试验与研究》2010年第1期9-14,共6页Gas Turbine Experiment and Research

基　　金：国家自然科学基金(50876023);国家重点基础研究发展(973)计划(2007CB210100);高等学校博士学科点专项科研基金(20060213007)

摘　　要：本文对采用孔隙射流的某大折转角压气机叶栅进行了实验研究,给出了不同攻角下叶栅流道内的静压分布、表面极限流线以及出口流场的气动参数,通过在不同叶高处开孔探讨了孔隙射流位置对大负荷扩压叶栅气动性能的影响。实验结果表明,孔隙位置对端壁静压的影响不大;开多孔方案对叶栅气动性能的影响要强于单孔方案;在设计攻角下,孔隙射流能够改善角区流动,同时降低叶片中部损失,单孔方案的最佳开孔位置位于25%相对叶高处,质量平均能量损失系数相对原形叶栅降低4.75%,开多孔方案中能量损失相对原形叶栅最多降低5.52%;在负攻角下,孔隙射流导致叶栅性能下降,而在正攻角下,孔隙射流大幅提高叶栅性能,能量损失系数相对原形叶栅最多降低12.7%。This paper presented an experimental investigation with air injection slot in a highly loaded linear compressor cascades, and detailed aerodynamic parameters of outlet flow field and end wall static pressure distribution at different incidences. It stressed on the influence of air injection slot position on aerodynamic performance of highly-loaded compressor cascade at different incidences. Results revealed that slot position had little effect on static pressure at the end wall. Multi-slot configurations had a greater effect on aerodynamic performance than one-slot configurations. At design incidence, air injection through slots improved flow at corner zone, and decreased loss near the mid span, the optimal slot position laid in 25 percent of blade span away from the end wall, the coefficient of mass-average total energy loss decreased 4.75 percent compared to the baseline case for one-slot configurations, and for multi-slot configurations, the coefficient of mass-average total energy loss decreased 5.52 percent. The aerodynamic performance of the cascade decreased at negative incidence. At positive incidence, the aerodynamic performance of the cascade improved significantly, the coefficient of total energy loss decreased 12.7 percent compared to the baseline case.

关 键 词：航空 航天推进系统 压气机叶栅 实验研究 孔隙射流 攻角 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]